High voltage system for satellites, aerospace vehicles, and the like



0 Aprll 12, 1966 F. E. NULL HIGH VOLTAGE SYSTEM FOR SATELLITES, AEROSPACE VEHICLES, AND THE LIKE I 3 Sheets-Sheet 1 Filed Oct. 12, 1962 Apnl 12, 1966 F. E. NULL 3,245,635

HIGH VOLTAGE SYSTEM FOR SATELLITES, AEROSPACE VEHICLES, AND THE LIKE Filed Oct. 12. 1962 5 Sheets-Sheet 2 m H l w JI MIIII N uell- 0 o o o o o o o o o Apnl 12, 1966 F. E. NULL 3,245,636

HIGH VOLTAGE SYSTEM FOR SATELLITES, AEROSPACE VEHICLES, AND THE LIKE Filed Oct. 12, 1962 3 Sheets-Sheet 5 Fig-E l H //2 l] ///3 l 1 2 L 15 Peon L/oS Fig"? United States Patent 3,245,636 HIGH VGLTAGE SYSTEM FOR SATELLITES, AEROSPACE VEHICLES, AND THE LllKE Fay E. Null, R0. Box 158, Shaiimar, Fiat. Filetl Oct. 12, 1962, Ser. No. 230,2?6 7 Claims. (Cl. 244-l) The invention described herein may be manufactured and used by or for the United States Government for governmental purposes without payment to me of any royalty thereon.

This invent-ion relates :to -a high voltage system for satellites and other vehicles launched into space and relates particularly to a voltage system capable of operation at extremely'high potentials.

In present day satellites and space craft in general it is becoming more apparent that considerably larger quantities of electrical energy than in the past will be required to fulfill scientific and tactical objectives. Thus, in the area of space systems a voltage genera-ting system of enlarged capacity and yet lower weight and volume than electrical power generators currently proven feasible would be immensely useful for fulfilling endeavors in numerous fields such as in the creation of space weapons. The supply of more sizeable quantities of electrical power in each case of development is, however, ordinarily hampered by problems which set a limit on expected im provements regarding weight per unit power.- Conventional dielectric or insulating elements associated commonly with high voltage power systems suffer somewhat from inherent limitations due to their size and propensity for leakage and make very inetficient use of whatever limited mounting space is available. It therefore becomes apparent that all elements contributing to the construction of high voltage supply systems destined for use in outer space must conveniently integrate into the satellite configuration and, while functioning in a medium of low atmospheric density, withstand extremely high potentials for short or extended periods of time.

Accordingly, an object of the invention is to provide a very high voltage system for aerospace vehicles.

A further object of the invention is the provision for aerospace vehicles or weapons of a high voltage system wherein the vacuum of space acts as the dielectric medium.

Still a further object of the invention is to provide a high voltage system for a body in space which is light, I

durable, compact, and limited to a few moving parts.

Yet a further object of the invention is the provision of a high voltage system extended outwardly of the satellite body once weightlessness is achieved. v

To accomplish the foregoing objects, a high voltage system for satellites constructed according to the invention comprises, in its most basic aspects, a pair of inner and outer cantilevered telescoping columns each formed of telescoping sections extendable from the satellite body to desired lengths with each telescoping section of the inner column and its companion telescoping section of the outer column independently supporting dielectrically separated elements with the vacuum of space constituting the dielectric.

Complete understanding of the invention and an introduction to other objects and features not specifically mentioned may be had from the following detailed description of a specific embodiment thereof when read in connection with the appended drawings in which:

FIG. 1 is a side elevation of the complete assembly which characterizes the high voltage generating system of the invention;

FIG. 2 is a view taken along line 22 .of FIG. 1;

FIG. 3 is a view similar to FIG. 1, but principally showing the inner column and its telescoping sections;

FIG. 4 is a view looking into the left end of FIG. 3;

"ice

FIG. 5 is a detailed view showing a latch arrangement used in the assembly illustrated in FIG. 1;

FIG. 6 is an electrical circuit diagramming the voltage generating aspect of the invention; and,

FIG. 7 is a schematic of the gate shown in FIG. 6.

Referring now to the drawings, wherein like reference characters designate like or corresponding parts throughout the views, and particularly to FIGS. 1 and 2, the high voltage generating system of the invention comprises two concentric telescoping columns which form a support base for the electrical components responsible for generating voltage. The outer column includes four orthogonal sections -10, 1'2, 14 and '16 of different internal cross-sectional area. The base section extends slightly into a'recess formed in one wall 22 of the body of a satellite or other space .vehicle and is fixed firmly to the satellite body in any suitable manner to create a cantilever suspension. A second wall 24 of the satellite has an orthogonal opening =24a dimensioned to permit extension of the columns from the satellite body. Each section of the outer column is suitable in dimension to admit the section adjacent to it so that when retracted into the satellite each succeeding section slides over the next preceding one. Interlocking of the various section of the outer column is performed by spring latches 2-6 exteriorly the outer column and similarly comprises four' telescoping sections designated 30, 32-, 34 and 36, in the order of their position relative to the satellite body. Base section 30 is disposed in concentric relation to the base section 10 of the outer column and similarly is :rigidly anchored to the wall 22 within the recess 20 provided therein. To resist bending load as might be caused by accelerations experi enced in tracking a target, the sections of the inner column have a cross-shaped or cruciate form which is better shown in FIGS. 2 and 4. With this construction, the center section 36 of the inner column is solid in appearance whereas the other three sections have internal cruciate openings which allow the sections to fit one inside the' other in sliding relationship. Attached adjacent the inner ends of sections '32, 34 and 36 are spring latches 38 of a form shown in FIG. 5. During extension of the inner column from the satellite the latches 38 successively engagecorresponding indentations 40 internally formed in sections 39, 32 and 34.

Prior to when positioning in an atmosphereless medium is achieved, both columns are retracted into the satellite. The mode of operation considered most convenient once the weightless state is entered is to extend the columns to the positions shown and to leave them extended for the life of the satellite. The operating mechanism for moving the columns comprises a telescoping push rod having four sections 40, 41, 42, and 43. The base section 40 rests at one end against wall 22 of the satellite and derives support from the wall 24 near its other end, while the outermost section 43 is joined in driving relation with an end cap 44 attached rigidly to section 16 of the outer column.

The end cap 44 is provided on its inner surface confronting the columns with superposed eyelet members 44a and 44b through which a pin 46 extends with clearance. Pin 46 also passes through an axially extending member 36a on section 36 of the inner column which lies centrally between members 44a and 44b on the end cap. A physical connection therefore exists between the inner and outer columns when the pin occupies the position shown. There is sufficient clearance between pin 46 and members 36a, it: and 44b so as to permit unrestricted passage of the pin through the members when desired. Thus, with the pin removed mechanical contact between the inner and outer columns is broken.

Sections 49, 41 and 42 of the push rod which are nearest the satellite body are tubular in form and when connected as shown establish a continuous passageway through which a compressible liquid or gas medium may be conveyed. It thus will be apparent that with section 43 of the push rod bearing against end cap 44 and section 49 firmly braced against wall 22 of the satellite, when a gas or liquid or other suitable medium under sufficient pressure is admitted to the passageway formed by the push rod sections, as through a valve 49, the end cap will be driven outwardly of the satellite body and carry with it section 16 of the outer column and section 36 of the inner column. The other sections of both columns emerge from the satellite body in succession upon engagement of the spring latches and associated grooves. Suitable spring latches 4'7 and corresponding indentations employed in the push rod mechanically link the sections of the push rod after being extended.

Following extension of the inner and outer columns under the action of the push rod, pin 46 may be'removed from members 36a, 44a and 44b in any suitable fashion. As particularly herein shown, one convenient method is to connect the pin to a pull wire 56 which runs on a roller 51 mounted on end cap 44. The other end of Wire 50 terminates in the space between the satellite walls wherein suitable control means, not shown, may be actuated to pull the pin when separation of the inner and outer columns is desired. A fractile member such as a drop of cement may be used to hold pin 46 in position as, for example, by lightly cementing the pin to one of the members 36a, 44a or 44b. Any suitable flexible member could be used in place of wire Stir and other suitable arrangements for terminating the connection made by pin 46 between the inner and outer columns will occur to those skilled in the art.

The respective sections of the inner and outer columns as well as the sections of the push rod are electrical insulators and may be made of quartz or other similar material.

After extension of the inner and outer columns and termination of the interlocking effect rendered by pin 46, the colums may tend to engage each other or become misaligned especially if the tolerances governing their spacing is small. Consequently, any misalignment of the columns will similarly effect supplementary parts mounted thereon. The disrupting effect of any small forces experienced in the weightless condition is overcome in the illustrated embodiment by four sets of permanent magnets so arranged that the magnets of each pair repel each other. The magnet pairs are references 52-52a, 53-53%], 54-5 and Sci-55a, the latter two magnet pairs more clearly appearing in FIG. 2. Of these, magnet 52 is attached to the wall of section 10 of the outer column and magnet 53 is attached to the wall of section 14, the latter magnet by means of a bracket 56. Still referring to the outer column, magnets 54 and 55 are attached to opposite walls of section 16, by brackets 57 and 58, respectively, thereby on the outer column placing one magnet adjacent each point of the cross-like configuration of the inner column. On the outer column, slots 60 (FIG. 2) which overlap each other are cut into and extend substantially the full length of the side walls of sections 10, 12 and 14 to allow passage of brackets 57 and '58 during extension of the outer column. Similarly, cut in the bottom walls of sections it), 12 are overlapping slots 62 through which bracket 56 moves as section 14 emerges from the enclosure formed by the satellite walls.

The magnets mounted on the sections of the inner column are spaced closely from those magnets on the outer column sections with which they form a pair. Section 30 of the inner column directly supports magnet 52a; from section 34 magnet 53a is mounted by a bracket 63; and magnets 54a and 5511 are attached to opposite sides of section 36 by means of corresponding brackets 64 and 65. Formed along the bottom walls of sections 36 and 32 are overlapping slots 66 (FIG. 2) which give access to bracket 63 as section 34 is extended. A similar construction of overlapping slots designated 67 is provided in opposite sides of sections 30, 32 and 34 while slots 67 receive magnet brackets 64 and 65 as section 36 is being ex tended.

Due to this arrangement of repelling magnets, the'columns are held in place by the action of symmetrical forces each 90 distant from an adjacent magnetic force. Such a suspension therefore allows the sections of the columns to be quite close to each other and insures that the columns are concentric in relation to each other. The necessity for the precise magnetic suspension which the aforementioned arrangement affords will be made apparent hereinbelow.

The magnetic separation forces of the suspension ar rangement in accordance with the invention may be further increased by attaching similar magnets to other corresponding sections in each of the columns and so magnetizing the magnets of each pair that they repel each other, all the while retaining the symmetry of the magnetic forces involved.

The established method of charging banks of capacitors in parallel and then simultaneously connecting them in series at the moment of the power requirement is used in the present invention for producing high voltage. Representative electrical components acting in conjunction with capacitive elements in the generation of the voltages desired are contained in four units 68, 69, 70 and 72 attached, respectively to sections 30, 32, '34 and 56 of the.

inner coiumns with one unit being placed in each quadrant. Thus, interference of the units during the telescoping movements is avoided. Inasmuch as no movement of unit 68 is required, it rests directly on section 30 in attached relation. Units 6), 7i) and 72 however are fastened to their respective supporting sections by means of pins or rods '74. In order to aliow telescoping movement of the inner column, sliding movement of the pins '74 must be uninhibited. Therefore, axially extending slots 75 Whose depth is determined by the positions of pins 74 are cut into the sides of sections 30, 32 and 34 in accordance with the position of each section in the group and the distance each must move while being extended. Exemplary of the construction illustrated is theiunit 70,

.placed in the fourth quadrant as seen in FIG. 4, whose mounting pins 74 attaching it to section 34 will slide relative to sections 34) and 32 in the overlapping slots 76 provided therein during movement of section 34 outwardly of the satellite body. With respect to sliding movement of the pins supporting the units mounted on sections32. and 36,- the slot construction is'similar to that just described.

Each of the units mounted on the sections of the inner column includes a set of stationarily mounted transformer secondary windings 78 (FIG. 3) and within each of the windings a tubular opening 80 dimensioned to admit a transformer primary winding 81 (FIG. 2) is formed. The primary-windings are supported by the sections of the outer column in similarly arranged sets and each extends with clearance' into one of the aforementioned tubular openings 8% which mark the location of the secondary windings. Support pins 82 which are an extension of the exterior cover housing the primary windings complete the attachment of the primary windings to the walls of the sections of the outer column. In the construction embodying the invention, the pins 82 which connect the primary windings to sections 12, 14 and 16 of the outer column are positioned to move in axially extending it will be seen in FIG. 2 that section 16, which is most distant from the satellite body after the columns are extended, supports primary windings 81 attached to pins 82 which slide freely relative to sections 10, 12 and 14 in overlapping slots 83 provided therein. A similar arrangementand operational mode during extension of the outer column applies to sections 12 and 14 which also are formed with slots on one side which receive pins 82. The slots in the section of the outer column wherever they appear do not extend into the rear overlapping portion of the sections so that a rigid corner construction is maintained at the unslotted rear portion of each section. The front end ofall sections except section 16 are held together by the unslotted rear end of the section next consecutively more distant from the satellite body.

' It will thus be understood that the primary and secondary windings on the telescoping columns are separated by a vacuum gap and that the uniform clearance necessary to insure electrical insulation is enforced by the balanced repulsion forces established by the aforementioned permanent magnet pairs. It is also important ionote that theprimary windings are inserted in the iopeningsprovided therefor .when the columns are assembled in the. retractedcondition and that no significant change in theposition of each winding pair occurs there- :after sincecorresponding sections of the columns which carry associated winding pairs move outwardly simultaneously when the columns are being extended. v A particular example of an arrangement for generating a comparatively great voltage suitable for use in the present invention is shown in FIG. 6. In this figure, 81 represents the primary windings supported on the sectional, structure of the outer telescoping column while the secondary windings contained in the units carried by thefin ne'r column, are designated 78 thus maintaining l identical numerical notations. An alternating voltage from a suitable potential source is impressed across terminals 84a and 84b of the primary winding 85 of a transformer 86 which may be iron-cored and, in a preferred embodiment. be designed for l kc. operation. The resulting voltage induced in the secondary winding 87 of transformer -86 charges a capacitor 88 through a rectifier 89. As the sinusoidal voltage from transformer 35 approaches its peak value, theaccumulated voltage on capacitor 88 breaks down a gas discharge tube 90 and capacitor 835 discharges through the primary winding 91 of a transformer 92 whose secondary winding 93 is connected in parallel with a capacitor 94. The resulting voltage which builds up on capacitor 94 breaks down a second gas discharge tube 95. Bucking rectifiers 96 and 97 connected in series with tube 95 and capacitor 94 direct the charge on capacitor 94 through primary windings 81 which, as shown, are also connected in series. By the voltages induced in secondary windings 78 a bank of capacitors C C C C are charged individually through rectifiers 98, 99, 102 and 103, respectively. The capacity load on the transformers which include primary and secondary windings 81 and 78 when reflected to the primary side is much greater than the capacity of the associated capacitor which is in series with the secondary winding so that repeated discharges of capacitor 94 into the seriesarranged primary windings are required to bring capacitors C C C and C to their optimum voltage. Rectifiers 96 and 97 prevent reversal of the charge on capacitor 94 when the steady state voltage is reached on capacitors C C C C and connect the primary windings in series. When the energy stored in the magnetic field of the transformers collapses, voltages are induced in the secondary windings that further add to the charge on the series-connected capacitors C C C and C The maximum charge developed on these latter capacitors are trapped by rectifiers 98, 99, 102 and 103. The successive discharges of capacitor 94 into the primary windings carried by the sectioned outer column thus creates a considerable quantity of voltage on each capacitor. Accordof each gate.

high voltage capacitors in series.

ing to the illustrated embodiment on each of 50 separately charged capacitors, a voltage of 2x10 volts may be stored using the vacuum of space as the dielectric.

When it is desired to use the stored voltage, capacitors C C C and C are connected in series by energizing electronic gates 104 activated by a suitable gate controller 105 capable of furnishing a negative voltage, which pe-rrnits the capacitors to discharge in series aiding relationship through output terminals 106 and 107, thereby supplying a burst of power to a space weapon or other controllable device receiving its input through the output terminals.

The dashed segments of the wires shown in FIG. 6 represent the location of other primary and secondary windings, and the related gate, capacitor and rectifier elements, which may be incorporated in the circuit in the number desired.

108 issuing an electron beam normally toward an anode 109 positively charged by one terminal of a direct current source 110, such as a battery shown, having its negative terminal returned to the electron gun via wire 112. The vacuum of space suffices for the internal construction Deflection plates113 and 114 the latter being grounded and the other having a connection to the output lead of the gate controller 105 occupy a beam defiection controlling position adjacent the electron gun. When a negative switching signal is applied to deflection plate 113, the electron beam is deflected toward a second anode 115 thereby completing a continuous electrical path through the gate between the two capacitors such as C and C interconnected by each gate. It will be understood that these capacitors represent the high voltage capacitance shown in FIG. -6. It will be appreciated further that the simultaneous action of all the gates places the The characteristics of the electron gates will be such as to withstand the high current supplied to any load placed across terminals 106 :and 107.

-age capacitors C C C and C as well as the gates 104 will be attached to the units in each quadrant so that a vacuum insulation would exist for the plates of each capacitor. Electrical wiring necessary to establish a given electrical circuit forms the only connection between the electrical apparatus supported by the inner and outer columns. Moreover, breakdown of the vacuum insulation under the conditions existing in the frictionless atmosphere of space becomes improbable in comparison to the weaknesses likely to develop in conventional dielectric materials if used instead at the voltages contemplated. Considerable savings in weight and volume are obtained from the preferred construction since the absolutely low atmospherrc pressure existing in the space environment outside :he satellite frees the designer from conventional restricions.

Although in the structure illustrated in the figures, each inner and outer column is divided into four sections, and the number of paired primary and secondary windings has figuratively been established at ten within each quadrant, thenu-mber of sections into which each column may be dtvrded and the number of transformers created by the paired primary and secondary windings is not material to 1. A voltage generating system for aerospace vehicles comprising two electrically nonconductive and concentric telescoping columns each having a base section attached rigidly to the vehicle, means for concurrently telescoping said columns outwardly of the vehicle once fiight into an atmosphereless region is achieved, and an electric power generator having a first part on one of said columns and a second part dielectrically separated from said first part by the vacuum of space on the other of said columns.

2 A high voltage system for aerospace vehicles having transient power needs of large magnitude comp-rising a pair of concentric telescoping electrically insulated colurnns attached to the vehicle at corresponding ends of the colunms, means for telescoping the sections of said columns outwardly of the vehicle upon arrival in a frictionless atmosphere, voltage generating components so mounted on the sections of each column that adjacent ones of said components not on the same column are dielectrical- 1y separated by a high vacuum environment, and permanent magnets mounted on both of said columns and by balanced mutual repulsion of repelling pairs of said mag nets maintaining magnetically the established vacuum separation of said components.

3. Voltage generating apparatus for aerospace vehicles destined for flight in atmosphereless regions comprising a pair of concentric telescoping members supported by the body of the vehicle and being sectionally extended therefrom when weightlessness is achieved, and electrically associated voltage handling elements mounted respectively, on one and the other of said columns,-the vacuum of space being sufficient to sustain electrical insulation between said voltage handling elements at the voltage level imposed.

4. A voltage generating system for aerospace vehicles destined for flight in the vacuum of space comprising a first telescoping column including slidably related sections of which a base section is fixed to the body of the vehicle,

a second telescoping column inwardly disposed of said first column and having slidably related sections of which a base section is fixed to said vehicle in concentricity to the base section of said first column, said sections of said first and second columns being of electrically insulating material, means for interlocking the sections of each column effective when the columns are extended, drive means for telescoping the sections of said columns outwardly of said vehicle into the atmosphereless region of space,

and voltage generating apparatus, parts of which are deployed on said first and second columns so that electrically associated parts not on the same column may rely on the vacuum of space as the mutually insulating medium.

5. A voltage generating system for space vehicles as in claim 4, in which each section of said first column is of orthogonal form.

6. A voltage generating system for space vehicles as in claim 4, in which each section of the second. column is of cruciate form and is surrounded by a companion section of said first column when both columns are extended.

7. A voltage generating system for aerospace vehicles destined for flight in a vacuum of space comprising a first telescoping column including slidably related orthogonal sections of which a base section is attached to the body of the vehicle, a second telescoping column inwardly disposed of said first column and including slidably related sections of cruciate form of which a base section is fixed to said vehicle in concentricity to the base section of said first column, said sections of said first and second columns being of electrically insulating material, latch and groove means forinterlocking sections of each column eifective when the columns are being extended, drive means for simultaneously telescoping the sections of both columns outwardly of said vehicle once fiightinto an atmosphereless environment is achieved, a first group of electrical components, first support pins each attaching components in the first group to extend inwardly from one wall of each section of saidv outer columns, a second group of electrical components, second support pins attaching at least one component in said second group to extend outwardly from one wall of each section of said outer column in electrical cooperating association proximity to one component in said first group, and slots developed in the sec: tions of said first and second columns so that the, support pins enter and slide through the slots during extension of said column.

References Cited by the Examiner UNITED STATES PATENTS 2,636,121 4/1953 Freas 343--902 2,835,548 5/1958 Baumann 244-1 LEWIS H. MYERS, Primary Examiner. 

1. A VOLTAGE GENERATING SYSTEM FOR AEROSPACE VEHICLES COMPRISING TWO ELECTRICALLY NONCONDUCTIVE AND CONCENTRIC TELESCOPING COLUMNS EACH HAVING A BASE SECTION ATTACHED RIGIDLY TO THE VEHICLE, MEANS FOR CONCURRENTLY TELESCOPING SAID COLUMNS OUTWARDLY OF THE VEHICLE ONCE FLIGHT INTO AN ATMOSPHERELESS REGION IS AHIEVED, AND AN ELECTRIC POWER GENERATOR HAVING A FIRST PART ON ONE OF SAID COLUMNS AND A SECOND PART DIELECTRICALLY SEPARATED FROM SAID FIRST PART BY THE VACUUM OF SPACE ON THE OTHER OF SAID COLUMNS. 